Results of numerical investigations of the influence of lift redistribution along the length of the airframe of an air-plane arrangement on the parameters of the acoustic shock produced by this arrangement and its aerodynamic characteristics are presented. The airplane arrangements investigated were constructed by disposition of wings in tandem at definite values of the aerodynamic lift and the lifting-surface area. The gasdynamic parameters of the flow near an arrangement were calculated by the numerical scheme based on the integral Euler equations, and the disturbed-pressure distribution at a large distance from the arrangement was determined using the quasi-linear theory. It is shown that the acoustic-shock level is substantially decreased in the case where there arises a middle-zone effect and an excess-pressure profile with an N-like shape. The arrangement of a supersonic airplane of weight 40 t making a cruise at a height H = 18 km and a Mach number Minfinite = 2.0, which makes it possible to decrease the acoustic shock produced by this airplane with no decrease in its lift-drag ratio, was determined.


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    Titel :

    Influence of lift redistribution along the length of a supersonic airplane on the acoustic-shock parameters


    Weitere Titelangaben:

    Einfluss der Auftriebsumverteilung längs eines Überschallflugzeuges auf die Schallstoßparameter


    Beteiligte:
    Fomin, V.M. (Autor:in) / Volkov, V.F. (Autor:in) / Chirkashenko, V.F. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    2007


    Format / Umfang :

    18 Seiten, 4 Bilder, 1 Tabelle, 10 Quellen




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch





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